Experimental Investigation of the Ignition Process of Solid Propellants in a Practical Motor Configuration
PRINCETON UNIV NJ DEPT OF AERONAUTICAL ENGINEERING
Pagination or Media Count:
A study of the ignition process of a composite solid propellant 80 wt- NH4ClO4 plus 20 wt- P-13 resin and additives was made in a combustion chamber whose configuration resembled that of a practical solid propellant motor. A small gas rocket chamber generated high temperature gaseous products, which in turn supplied the ignition energy to the internal surface of a cylindrical thin-web, case-bonded solid propellant grain. The ignition delay, the time between ignition of the gas igniter and the first ignition of the solid propellant grain, was measured as a function of the temperature, pressure, the chemical reactivity of the hot gases, and the velocity of these gases over the solid propellant surface. The ignition times were measured by means of a strain-gage pressure transducer inserted in the solid propellant motor chamber.
- Combustion and Ignition
- Solid Rocket Propellants